過流翼型 的英文怎麼說

中文拼音 [guòliúyìxíng]
過流翼型 英文
flow profile
  • 過 : 過Ⅰ動詞[口語] （超越） go beyond the limit; undue; excessiveⅡ名詞（姓氏） a surname
  • 流 : Ⅰ動1 （液體移動; 流動） flow 2 （移動不定） drift; move; wander 3 （流傳; 傳播） spread 4 （向壞...
  • 翼 : Ⅰ名詞1 （翅膀） the wing of a bird 2 （像翅膀的東西） the wing of an aeroplane etc : 鼻翼 wing of...
  1. The stability of the tiltrotor in the heli copter mode is analyzed aiming t a semi span soft - inplane tiltrotor model with an elastic wing

    集成了非定常動態人流方程與傾轉過渡狀態的多體動力學力程，建立了傾轉旋翼機時域非定常氣彈耦合分析模型。
  2. On the basis of axial vortex theory, the aerodynamic performance of tilt - rotor model has been built, and using it to analyze the aerodynamic performance of xv - 15, comparing to the actual data to prove the model ’ s validity, finally studied the variety of aerodynamic performance relative to the variable rotor diameter

    以軸向渦流理論為基礎，建立了適合於傾轉旋翼機氣動分析模型，以xv - 15傾轉旋翼機作為算例，通過結果的對比，表明本文的氣動模型能較好的分析傾轉旋翼機的氣動性能，並在氣動性能的基礎上分析了直徑變化對傾轉旋翼機氣動性能的影響。
  3. The main work in this paper includes three parts : the theory research on partially - cavitating and super - cavitating axisymmetric bodies, the numerical computations and experimental investigations on partially - cavitation and super - cavitation on axisymmetric bodies. after finishing the study of theory and experiment on the partially - cavitation and super - cavitation for axisymmetric body, i use the potential flow theory to build the mathematical model on the partially - cavitation and super - cavitation for axisymmetric body. many cavity wake models, such as pressure recovery close model, riabouchinsky model and re - entrant jet model, are studied seriously

    本文在深入研究了回轉體局部空化與超空化理論及實驗結果的基礎上，基於勢流理論，建立了回轉體局部空泡和超空泡流場的基本數學模型，通過對kinnas和fine 、 uhlman以及jiedang和gertkuiper等人基於二維水翼提出的壓力恢復閉合模型、鏡像板模型和回射流模型等空泡尾流模型進行了逐一的研究分析，發現其中的壓力恢復閉合模型較適用於模擬回轉體空泡尾部流場，並選用此空泡尾流模型作為求解回轉體空化流場正問題與逆問題的數學模型的組成部分。
  4. Only clouds of points instead of grids are distributed over the computational domain and the spatial derivatives are estimated using a least - square curve fit on local clouds of points. the paper gives discrete form for euler equations on base of gridless method, and adopts five steps runge - kutta scheme for time - marching. the numerical results have been obtained for the 2 - d flows over airfoils or multi - element airfoils using the method presented

    本文首先對無粘euler方程進行無網格離散，並運用顯式runge - kutta格式推進求解，成功地數值模擬了二維單段和多段翼型的繞流；在此成功的基礎上通過在euler方程的右端加入粘性項，使求解方程變為層流navier ? stokes方程，得到了翼型繞流，數值結果顯示出粘性的影響。
  5. In this paper, the boundary layer characteristics of a supercritical airfoil is researched in wind tunnel. from the start to control boundary layer separation and to improve aerodynamics characteristics of this airfoil, three kinds of trapezoid, delta and airfoil shaped vortex generators are designed based on traditional, sub boundary layer and micro - vortex generators conceptual design. it include as follows : 1

    研究工作中，從控制該翼型附面層分離、提高大迎角氣動性能的角度出發，通過風洞實驗研究，研究了該翼型的附面層特性和氣動性能，針對其附面層特性，給出了梯形、三角形和翼型式三種渦流發生器設計方案，為下一步研究工作奠定了堅實基礎。
  6. This paper explored the micro pressure sensor that is used for the measurement of distributed pressure at the surface of smart - skin. firstly, established the surface pressure model according to the aerodynamic properties, defined the optical measurement system that based on intensity modulation principle, discussed the components of this system and theoretical analyzed its measurement theory in detail

    首先，根據空氣流動的基本規律給出機翼表面壓力分布圖，通過對光學式微型壓力傳感器的理論分析，採用強度調製法測量飛機機翼表面的壓力並建立基於此方法的光學測量系統模型，得到了壓力與敏感膜片變形以及光電轉換輸出能量之間的關系。
  7. Loss of head is minimized by the balanced disc and its " aerofoil " design. streamlined body without pockets contributes to straight - through flow

    通過平衡閥瓣及其「翼型」結構，將水頭損失（或位差損失）降到最小程度。流線型閥體，不再需要凹穴來幫助流體直線流通。
  8. In chapter 6, a new idea for simulating rotor bvi noise experiment is presented using a scissors rotor configuration with the vertical separation between a pair of rotors, based upon the fact that the important aerodynamic feature of this scissors rotor configuration is its close blade - vortex encounter. and the models and facilities designed for the bvi noise experiment are given

    在第六章，基於槳-渦靠近通過是非共面剪刀式布置旋翼流場的一個重要特徵，提出了使用剪刀式布置旋翼來模擬旋翼槳-渦干擾噪聲實驗的新構想，並設計了用於噪聲實驗的模型。
  9. We studied four eddy viscosity models ( evm ) and three nonlinear easm models in detail. the two - equation turbulence models are validated through simulating the flow fields over flat plate, airfoils and onera m6 wing. the capabilities of different turbulence models are accessed in this study

    加入兩方程湍流模型后，通過對平板、翼型、 oneram6機翼等繞流流場的數值計算，驗證了加入的各湍流模型的準確性，測試了它們對不同湍流流場的預測能力。
  10. The design method used here is relatively independent with the direct procedure of calculation of flow solver by finite volume method, other flow solvers can also be easily coupled with this design method

    本文的設計方法與正計算過程有相對的獨立性，可分別和不同的流場分析程序耦合，形成翼型設計軟體。
  11. However, typically we fit just three and this can drop to as few as two for a low - downforce circuit, such as monza in italy

    前翼的相對適應賽道的形狀並非空穴來風，而是通過一個名為「計算機氣流編輯器」的程序的運算后得來的，而這個運算系統同時和風洞模型的長時間測試緊密相關。
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